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Two dimensional cold air cascade study of a film cooled turbine stator blade. 2: Experimental results of full film cooling testsThe effect of full film cooling on the performance of a turbine stator blade was studied in a two-dimensional cascade. The blade contained 12 rows of coolant holes, 6 rows on the suction surface and 6 on the pressure surface. Separate tests were first made with coolant ejection from each of the 12 rows. Then successive tests were made with various combinations of coolant rows open, including full film cooling. The principal results are presented in terms of primary-air efficiency as a function of coolant fraction. In addition, the efficiency results of the multirow tests are compared with the multi-row efficiency predicted by adding the single-row results.
Document ID
19750006687
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Prust, H. W., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-3153
E-8052
Accession Number
75N14759
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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